CN107100681A - Secondary system for gas-turbine unit - Google Patents
Secondary system for gas-turbine unit Download PDFInfo
- Publication number
- CN107100681A CN107100681A CN201710085941.3A CN201710085941A CN107100681A CN 107100681 A CN107100681 A CN 107100681A CN 201710085941 A CN201710085941 A CN 201710085941A CN 107100681 A CN107100681 A CN 107100681A
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- CN
- China
- Prior art keywords
- gas
- turbine unit
- outside
- secondary system
- source
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/04—Cleaning involving contact with liquid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/002—Cleaning of turbomachines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B9/00—Cleaning hollow articles by methods or apparatus specially adapted thereto
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/34—Turning or inching gear
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/72—Maintenance
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Cleaning By Liquid Or Steam (AREA)
- Cleaning In General (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The disclosure is used for the secondary system (102) of clean gas turbogenerator (10) for a kind of.Start source (104) in the outside that secondary system (102) includes one or more engine shafts for being mechanically coupled to gas-turbine unit (10).Therefore, outside starts source (104) to be configured to rotate one or more axles (30,34).Secondary system (102) also includes cleaning equipment (105), its one or more axle (30,34) for being configured to start source (104) to make gas-turbine unit (10) in outside implements cleaning procedure while rotation on gas-turbine unit (10).
Description
Technical field
The present invention relates generally to gas-turbine unit, and more particularly relates to the auxiliary of gas-turbine unit
Help cleaning systems.
Background technology
Gas-turbine unit generally includes compressor section, burning block, turbine and the row with crossfire order
Gas section.In operation, air enter compressor section entrance, in the compressor section, it is one or more axial direction or
Centrifugal compressor gradually reduces air, until it reaches burning block.Fuel is mixed simultaneously in burning block with the air of compression
And burn, to provide burning gases.Burning gases are transmitted through being limited to the hot gas path in turbine from burning block,
And then discharged from turbine via exhaust section.
In particular configuration, turbine is included with high pressure (HP) turbine of crossfire order and low pressure (LP) turbine.HP whirlpools
Wheel and LP turbines include various rotatable turbine components, such as armature spindle, by armature spindle install or carry in addition rotor disk,
The turbo blade for being installed on the periphery of disk and being radially extended from it, and various static turbine component such as stator vanes or spray
Mouth, turbine shroud and engine frame.Rotatable and static turbine component at least partially defines the heat through turbine
Gas path.For example, gas turbine wheel blade or blade generally have air foil shape, it is designed to the heat of flow path gas
The machinery rotation of rotor can be converted into kinetic energy.When combustion gas flow passes through hot gas path, heat energy is passed from burning gases
It is handed to rotatable and static turbine component.Such gas-turbine unit is generally used on aircraft.
The efficiency of gas-turbine unit is reduced due to the environmental pollution accumulation in engine component.For example, compressor
Blade and stator can be gathered by hydrocarbon deposit, dirt, salt and corrosivity residue, have impact on their air pertormance
Energy.Such deposit can increase effluent air temp and fuel is used, and reduce the surge margin of engine.
Therefore, water wash procedures are generally periodically used in gas-turbine unit.Typical water wash procedures are included with a large amount of
Water and sometimes a small amount of cleaning agent periodically washing engine.In addition, the starter of gas-turbine unit is typically in the washing phase
Between with approximate 20%rpm engine ons.
However, starter working cycles typically need a certain amount of downtime between each starting of engine, example
Such as, 60 (60) minutes between every secondary starting in three (3).Due to such limitation of starter working cycles, therefore gas turbine starts
The washing ability of machine is also to be limited.
In view of foregoing, the secondary system for gas-turbine unit for avoiding starter working cycles will be favourable
's.
The content of the invention
Aspects and advantages of the present invention will be set forth in part in the description that follows, or can from be described as it will be evident that or
Learning by doing of the invention can be passed through.
In one aspect, the disclosure is directed to a kind of secondary system for clean gas turbogenerator.Auxiliary is clear
Start source in the outside that clean system includes one or more engine shafts for being mechanically coupled to gas-turbine unit.Therefore,
Start source structure into rotating one or more axles in outside.Secondary system also includes cleaning equipment, and it is configured to outside
Implement cleaning on gas-turbine unit while starting source to rotate one or more axles of gas-turbine unit in portion
Program.
In another aspect, the disclosure is directed to a kind of method for clean gas turbogenerator.This method includes will
Outside starts source to be mechanically coupled to one or more engine shafts of gas-turbine unit, wherein outside start source structure
Rotated into one or more axles are made.Therefore, this method include via it is outside start source make one of gas-turbine unit or
More axles are rotated.This method is additionally included in while axle is rotated implements cleaning via cleaning equipment on gas-turbine unit
Program.
In another aspect, the disclosure is directed to a kind of gas turbine assembly.Gas turbine assembly includes
Gas-turbine unit with one or more engine shafts, and it is mechanically coupled to one or more engine shafts
Outside start source.Therefore, source structure is started into rotating one or more axles in outside.Gas turbine assembly is also wrapped
Cleaning equipment is included, it is configured to while the outside one or more axles for starting source to make gas-turbine unit are rotated in combustion
Implement cleaning procedure on gas eddy turbine.
A kind of secondary system for clean gas turbogenerator of technical scheme 1., the launching system includes：
Source is started in outside, and it is mechanically coupled to one or more engine shafts of the gas-turbine unit, described outer
Start source structure into rotating one or more axle in portion；And
Cleaning equipment, it is configured to start in the outside source to make one an or more axle for the gas-turbine unit
Implement cleaning procedure on the gas-turbine unit while rotation.
Secondary system of the technical scheme 2. according to technical scheme 1, it is characterised in that start source in the outside
In the hand starting port for being installed to the starter of the gearbox of the gas-turbine unit or the gas-turbine unit
At least one in.
Secondary system of the technical scheme 3. according to technical scheme 1, it is characterised in that start source in the outside
Including at least one in crank, hydraulic motor, air driven motor, water-driven motor or gas energised motor.
Secondary system of the technical scheme 4. according to technical scheme 1, it is characterised in that start source in the outside
The gas-turbine unit is not connected to when the gas-turbine unit is operated in normal manipulation mode.
Secondary system of the technical scheme 5. according to technical scheme 1, it is characterised in that the cleaning equipment bag
Conveying equipment for fluid substances is included, it is configured to the cleaning liquid including at least water being incorporated into the gas-turbine unit.
Secondary system of the technical scheme 6. according to technical scheme 5, it is characterised in that the cleaning liquid is also
Including cleaning agent.
Secondary system of the technical scheme 7. according to technical scheme 5, it is characterised in that the fluid conveying is set
It is standby to include at least one nozzle.
Secondary system of the technical scheme 8. according to technical scheme 1, it is characterised in that the gas turbine hair
Motivation includes aircraft engine.
Secondary system of the technical scheme 9. according to technical scheme 8, it is characterised in that the aircraft starts
Machine is installed on board the aircraft during the cleaning procedure.
A kind of method for clean gas turbogenerator of technical scheme 10., methods described includes：
By the outside one or more engine shafts for starting source to be mechanically coupled to the gas-turbine unit, the outside
Start source structure into rotating one or more axle；
Source is started to rotate one or more axle of the gas-turbine unit via the outside；And
Implement cleaning procedure on the gas-turbine unit via cleaning equipment while the axle is rotated.
Method of the technical scheme 11. according to technical scheme 10, it is characterised in that methods described also includes will be described
Outside start source be installed to the gas-turbine unit gearbox starter or the gas-turbine unit it is hand
Start at least one in port.
Method of the technical scheme 12. according to technical scheme 10, it is characterised in that start source to include song in the outside
At least one in handle, hydraulic motor, air driven motor, water-driven motor or gas energised motor.
Method of the technical scheme 13. according to technical scheme 10, it is characterised in that methods described is additionally included in described
When gas-turbine unit is operated in normal manipulation mode, the outside is set to start source to break with the gas-turbine unit
Open.
Method of the technical scheme 14. according to technical scheme 10, it is characterised in that methods described also includes via institute
Cleaning liquid including at least water is transported in the gas-turbine unit by the conveying equipment for fluid substances for stating cleaning equipment.
Method of the technical scheme 15. according to technical scheme 10, it is characterised in that methods described also includes control institute
State the duration of cleaning procedure.
Method of the technical scheme 16. according to technical scheme 10, it is characterised in that the gas-turbine unit bag
Aircraft engine is included, wherein the aircraft engine is installed on board the aircraft during the cleaning procedure.
A kind of gas turbine assembly of technical scheme 17., the gas turbine assembly includes：
Gas-turbine unit, it has one or more engine shafts；
Source is started in outside, and it is mechanically coupled to one or more engine shaft, and source structure is started into making in the outside
One or more axle is rotated；And
Cleaning equipment, it is configured to start in the outside source to make one an or more axle for the gas-turbine unit
Implement cleaning procedure on the gas-turbine unit while rotation.
Gas turbine assembly of the technical scheme 18. according to technical scheme 17, it is characterised in that described outer
Portion start source be installed to the gas-turbine unit gearbox starter or hand of the gas-turbine unit
In at least one in moved end mouthful.
Gas turbine assembly of the technical scheme 19. according to technical scheme 17, it is characterised in that described outer
Source is started to include at least one in crank, hydraulic motor, air driven motor, water-driven motor or gas energised motor in portion.
Gas turbine assembly of the technical scheme 20. according to technical scheme 17, it is characterised in that described outer
Portion starts source to be not connected to the gas turbine when the gas-turbine unit is operated in normal manipulation mode to start
Machine.
The feature of these and other, aspect and the advantage of the present invention will become more with reference to the following description and the appended claims
It is good to understand.The accompanying drawing for being incorporated in this manual and constituting the part of this specification shows embodiments of the invention, and
It is used for the principle for explaining the present invention together with description.
Brief description of the drawings
Subject of the present invention is recognized as to particularly point out and be distinctly claimed in the latter end of specification.However,
The present invention can be best understood by by referring to the following description carried out together with accompanying drawing, in the figure：
Fig. 1 shows that the section of one embodiment of the gas-turbine unit that can be used in aircraft according to the disclosure is regarded
Figure；
Fig. 2 shows the signal of one embodiment of the gas turbine assembly that can be used in aircraft according to the disclosure
Figure；
Fig. 3 shows an implementation of the cleaning equipment of the secondary system for gas-turbine unit according to the disclosure
The block diagram of example；And
Fig. 4 shows the flow chart of one embodiment of the method for clean gas turbogenerator according to the disclosure.
List of parts
10 gas-turbine units
12 cener lines
14 core gas-turbine units
16 fan sections
18 shells
20 annular entries
22 booster compressors
24 high pressure compressors
25 gearboxes
26 burners
28 high-pressure turbines
30 high-voltage drive axles
32 low-pressure turbines
34 low pressure rotor drive axles
36 exhaust nozzles
37 deceleration devices
38 rotor assembly
40 fan hubs
42 exit guide blades
44 fan rotor blades
46 downstream sections
48 air ducts
50 air streams
52 entrances
54 air streams
56 air streams
58 air streams
60 combustion products
62 close to port
62A is close to port
62B is close to port
66 turbine nozzles
68 rotary turbine blades
70 nozzle guide vanes
72 arch are in addition
Band in 74 arch
76 turbine shrouds
78 nozzle guide vanes
100 gas turbine assemblies
102 secondary systems
Start source outside 104
105 cleaning equipments
106 conveying equipment for fluid substances
108 cleaning liquid
110 water
112 cleaning agents
114 valves
116 controllers
200 methods
202 method and steps
204 method and steps
206 method and steps.
Embodiment
Embodiments of the invention are reference will now be made in detail to now, its one or more example is shown in the drawings.Each example
Via explaination, the present invention is provided, without limiting the present invention.In fact, be evident that to those skilled in the art,
Can various modifications may be made in the present invention and modification, without departing from the scope of the present invention or spirit.For example, being illustrated or described as one
The feature of the part of individual embodiment can be used together to produce another embodiment with another embodiment.It is therefore intended that this
Appended claims and such remodeling in the range of their equivalent and modification are included into invention covering.
As used in this article, term " first ", " second " and " the 3rd " can be interchangeably used, by a component
Distinguished with another, and be not intended to the position for representing individual member or importance.
Term " upstream " and " downstream " refer to the relative direction relative to the fluid stream in fluid passage.For example, " upstream "
Refer to the direction of fluid stream certainly, and " downstream " refers to the direction that fluid is flow to.
Generally, the disclosure is directed to the secondary system for clean gas turbogenerator.Secondary system bag
Start source in the outside for including one or more engine shafts for being mechanically coupled to gas-turbine unit.Therefore, outside is started
Source structure is rotated into making one or more axles when cleaning equipment implements cleaning procedure on gas-turbine unit.
Therefore, present disclose provides do not exist in many advantages of the prior art.More specifically, conventional wing supernatant
Clean and/or washing ability is limited by starter and/or APU operational requirements.Therefore, the outside of the disclosure starts source to be greatly enhanced
The cleaning of gas-turbine unit and/or washing ability, because there is unrestricted cycle duration, and are not present
Waiting period between circulation.In addition, source is started by using outside, (multiple) speed for rotating engine shaft and duration
It can extend, to allow the longer water washing operations in the state of increase scope.Therefore, the disclosure can extend the wing for engine
The upper time, and will eventually lead to less performance-relevant engine removing.
Referring now to accompanying drawing, Fig. 1 is shown to be started according to the gas turbine that can be used in aircraft of the aspect of this theme
The sectional view of one embodiment of machine 10, wherein engine 10 are shown as having extends through its longitudinal direction or axle for reference purposes
To cener line 12.Generally, engine 10 may include that core gas-turbine unit (is generally referred to by reference 14
Show) and be positioned on trip fan section 16.Core engine 14 can generally include the substantially pipe for limiting annular entry 20
The shell 18 of shape.In addition, shell 18 can also surround and support booster compressor 22, it is used for the sky by core engine 14 is entered
The pressure of gas increases to first pressure level.High-pressure multi-stage Axial Flow Compressor 24 can then be received from booster compressor 22 and pressurizeed
Air, and further increase the pressure of such air.Burning can then be flowed to by leaving the forced air of high pressure compressor 24
Device 26, fuel is ejected into burner 26 in forced air stream, wherein the mixture of gained burns in burner 26.High energy
Combustion product is guided to first (high pressure) turbine 28 from burner 26 along the hot gas path of engine 10 to be used for via the first (height
Pressure) the driving high pressure compressor 24 of power transmission shaft 30, and then guide to second (low pressure) turbine 32 and be used for via generally with the
One power transmission shaft 30 coaxial second (low pressure) power transmission shaft 34 driving booster compressor 22 and fan section 16.In the driving He of turbine 28
After each in 32, combustion product can eject offer propulsion jet thrust from core engine 14 via exhaust nozzle 36.
In addition, as shown in fig. 1, the fan section 16 of engine 10 can generally include rotatable tube-axial fan and turn
Sub-component 38, it is configured to be wrapped by ring-type fan shell 40.It would be recognized by those skilled in the art that, fan hub 40 can be constructed
Supported on core engine 14 by multiple circumferentially spaced exit guide blades 42 substantially radially extended.Thus,
Fan hub 40 can surround the fan rotor blade 44 corresponding with its of fan propeller component 38.In addition, the downstream section of fan hub 40
46 can extend on the outer portion of core engine 14, to limit the pair or bypath air that provide additional propulsion jet thrust
Conductance pipe 48.In addition, gas-turbine unit 10 may include gearbox 25.In addition, gearbox 25 can be constructed in gas turbine hair
At any suitable position in motivation 10, but it is typically mounted on fan hub 40 or the lower section of high pressure compressor 24.
It is to be appreciated that in several embodiments, second (low pressure) power transmission shaft 34 can directly be connected in fan and turn
Sub-component 38, to provide direct drive construction.Alternately, second driving shaft 34 can be via deceleration device 37 (for example, reducing gear
Wheel or gearbox) it is connected in fan propeller component 38, constructed with providing driving indirectly or gear driving.Such (multiple) dresses that slow down
Put and can also desirably or require to be located between any other suitable axle and/or rotating shaft in engine 10.
During the operation of engine 10, it will be appreciated that initial air stream (being indicated by arrow 50) can be by fan
The associated entrance 52 of shell 40 enters engine 10.Air stream 50 is subsequently passed through fan blade 44, and is divided into and moving through
The first compressed air stream (being indicated by arrow 54) of conduit 48 and the second compressed air stream of entrance booster compressor 22 are (by arrow
56 indicate).The pressure of second compressed air stream 56 then increases, and enters high pressure compressor 24 (such as being indicated by arrow 58).
It is after mixing and burn with fuel in burner 26, combustion product 60 leaves burner 26, and flows through first
Turbine 28.Hereafter, combustion product 60 flows through the second turbine 32, and leaves exhaust nozzle 36, is used for engine to provide
10 thrust.
Referring now to Fig. 2, the schematic diagram of one embodiment of gas turbine assembly 100 is shown.It is more specific and
Speech, as indicated, gas turbine assembly 100 includes gas-turbine unit 10, and is configured to not operate in engine
The secondary system 102 of Shi Qingjie engines 10.In certain embodiments, as mentioned, gas-turbine unit 10 can be wrapped
Include aircraft engine.Therefore, in such embodiment, aircraft engine can pacify during described cleaning procedure herein
Dress is on board the aircraft.In addition, as indicated, gas-turbine unit 10 has one or more engine shafts 30,34, Yi Jiji
Start source 104 in the outside for being connected in (multiple) engine shaft 30,34 tool.More specifically, in certain embodiments, outside hair
Dynamic source 104 may include crank (manually or automatically), hydraulic motor, air driven motor, water-driven motor, gas energised motor,
Or any other suitable launch device.In addition, outside, to start source 104 to be arranged on any suitable in gas-turbine unit 10
At the position of conjunction, including but for example, the starter of gearbox 25, or gas-turbine unit 10 hand starting port.Therefore,
Source 104 is started to be configured to not operate in its normal manipulation mode (that is, being driven by engine starter) in engine 10 in outside
When rotate (multiple) engine shaft 30,34.In addition, for some embodiments, outside start source 104 engine 10 at it just
Gas-turbine unit 10 is not connected to when being operated in normal operator scheme.On the contrary, during normal manipulation mode, starter
Working cycles are configured to rotate engine shaft 30,34.
In addition, as shown in Figures 2 and 3, secondary system 102 may also include cleaning equipment 105, and it is configured in outside
Implement while starting source 104 to rotate (multiple) axle 30,34 of gas-turbine unit 10 on gas-turbine unit 10
Cleaning procedure.More specifically, as shown in Figure 3, cleaning equipment 105 may include conveying equipment for fluid substances 106, and it is configured near
The cleaning liquid 108 comprising water 110 is incorporated into gas-turbine unit 10 less.In certain embodiments, as shown in Figure 3,
Cleaning liquid 108 may also include any suitable cleaning agent of any suitable amount.For example, as shown in Figure 3, cleaning agent 112 can
Water 110 is added on demand via valve 114.Thus, some wash cycles can only include water 110, but other wash cycles
It may include the water 110 mixed with cleaning agent 112.
In addition, as shown in Figure 2, equipment for liquid transportation 106 may include nozzle 108, or any other suitable fluid is defeated
Send device.It should be appreciated that any amount of nozzle 108 may include in cleaning equipment 105.For example, as shown in Figure 2,
Total of five nozzle 108 is included in cleaning equipment 105.In a further embodiment, more than five nozzles 108 or less than five
Nozzle 108 may include in cleaning equipment 105.
Referring now to Fig. 4, the flow of one embodiment of method 200 for clean gas turbogenerator 10 is shown
Figure.As shown at 202, method 200 include by it is outside start source 104 be mechanically coupled to one of gas-turbine unit 10 or
More engine shafts 30,34, wherein outside start source 104 to be configured to rotate axle 30,34.As shown at 204, this method is passed through
Source 104 is started to rotate the axle 30,34 of gas-turbine unit 10 by outside.As shown at 206, method 200 is included in axle 30,
34 implement cleaning procedure via cleaning equipment 105 while rotation on gas-turbine unit 10.
In one embodiment, method 200 may also include the starting for starting source 104 to be installed at least gearbox 25 outside
In the hand starting port of machine or gas-turbine unit 10.In a further embodiment, method 200 may additionally include combustion gas whirlpool
Turbine 10 makes outside start source 104 to be disconnected with gas-turbine unit 10 when being operated in normal manipulation mode.Therefore, exist
In some embodiments, outside starts source 104 to be configured to only operate when gas-turbine unit 10 is closed.
In an additional embodiment, may also include will at least via the conveying equipment for fluid substances 106 of cleaning equipment 105 for method 200
Cleaning liquid 108 comprising water 110 is transported in gas-turbine unit 10.
In addition, in certain embodiments, method 200 may include the duration for controlling cleaning procedure.More specifically, by
Start source 104 outside gas-turbine unit 10 in outside, and independent of engine starter, therefore cleaning procedure may depend on
The state of turbogenerator 10 is maximized to any suitable length, without the washing energy power restriction by starter working cycles.
For example, as shown in Figure 2, secondary system 102 may include controller 116, its be configured to control it is outside start source 104 and/
Or cleaning equipment 105.In an additional embodiment, outside starts source 104 and cleaning equipment 105 manually to control.
The written description, to disclose of the invention (including optimal mode), and also makes those skilled in the art using example
Can put into practice the present invention (including manufacture and using any device or system and perform any method being incorporated to).The present invention's can
The scope of the claims is defined by the claims, and may include other examples that those skilled in the art expect.If these other realities
Example includes the structural detail different not from the literal language of claim, or if these other examples include and claim
Equivalent structural elements of the literal language without marked difference, then these other examples be intended within the scope of the claims.
Claims (10)
1. one kind is used for the secondary system (102) of clean gas turbogenerator (10), cleaning systems (102) bag
Include：
Source (104) is started in outside, and it is mechanically coupled to one or more engines of the gas-turbine unit (10)
Source (104) is started to be configured to rotate one or more axle (30,34) in axle (30,34), the outside；And
Cleaning equipment (105), it is configured to start source (104) to make the described of the gas-turbine unit (10) in the outside
One or more axles (30,34) implement cleaning procedure while rotation on the gas-turbine unit (10).
2. secondary system (102) according to claim 1, it is characterised in that start source (104) to install in the outside
Starter or the hand starting end of the gas-turbine unit (10) to the gearbox of the gas-turbine unit (10)
In at least one in mouthful.
3. secondary system (102) according to claim 1, it is characterised in that start source (104) to include in the outside
At least one in crank, hydraulic motor, air driven motor, water-driven motor or gas energised motor.
4. secondary system (102) according to claim 1, it is characterised in that start source (104) in institute in the outside
State when gas-turbine unit (10) is operated in normal manipulation mode and be not connected to the gas-turbine unit (10).
5. secondary system (102) according to claim 1, it is characterised in that the cleaning equipment (105) includes stream
Body conveying equipment (106), it is configured to the cleaning liquid (108) including at least water being incorporated into the gas-turbine unit
(10) in.
6. secondary system (102) according to claim 5, it is characterised in that the cleaning liquid (108) also includes
Cleaning agent.
7. secondary system (102) according to claim 5, it is characterised in that conveying equipment for fluid substances (106) bag
Include at least one nozzle.
8. secondary system (102) according to claim 1, it is characterised in that the gas-turbine unit (10)
Including aircraft engine.
9. secondary system (102) according to claim 8, it is characterised in that the aircraft engine is described
Installed on board the aircraft during cleaning procedure.
10. one kind is used for the method for clean gas turbogenerator (10), methods described includes：
Source (104) is started to be mechanically coupled to one or more engine shafts of the gas-turbine unit (10) outside
Source (104) is started to be configured to rotate one or more axle (30,34) in (30,34), the outside；
Via the outside start source (104) make the gas-turbine unit (10) one or more axle (30,
34) rotate；And
Implement while the axle (30,34) is rotated via cleaning equipment (105) on the gas-turbine unit (10)
Cleaning procedure.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US15/047,737 US20170239692A1 (en) | 2016-02-19 | 2016-02-19 | Auxiliary Cleaning System for Gas Turbine Engines |
| US15/047737 | 2016-02-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107100681A true CN107100681A (en) | 2017-08-29 |
Family
ID=58016633
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710085941.3A Pending CN107100681A (en) | 2016-02-19 | 2017-02-17 | Secondary system for gas-turbine unit |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20170239692A1 (en) |
| EP (1) | EP3208430A1 (en) |
| CN (1) | CN107100681A (en) |
| CA (1) | CA2957487A1 (en) |
| SG (1) | SG10201700926TA (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107514312A (en) * | 2017-09-04 | 2017-12-26 | 中国航发南方工业有限公司 | The control device and control method of the pneumatic cleaning magnetic valve of combustion engine |
| CN111734689A (en) * | 2020-07-02 | 2020-10-02 | 中国航发常州兰翔机械有限责任公司 | Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BR122020021156B1 (en) | 2013-10-02 | 2023-12-19 | Aerocore Technologies Llc | METHOD FOR SCHEDULING FOAM CLEANING OF A GAS TURBINE ENGINE |
| US11643946B2 (en) | 2013-10-02 | 2023-05-09 | Aerocore Technologies Llc | Cleaning method for jet engine |
| US11530635B2 (en) * | 2018-12-11 | 2022-12-20 | Raytheon Technologies Corporation | Fluid injection systems for gas turbine engines |
| GB201914723D0 (en) | 2019-10-11 | 2019-11-27 | Rolls Royce Plc | Cleaning system and a method of cleaning |
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- 2017-02-09 CA CA2957487A patent/CA2957487A1/en not_active Abandoned
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| CN107514312A (en) * | 2017-09-04 | 2017-12-26 | 中国航发南方工业有限公司 | The control device and control method of the pneumatic cleaning magnetic valve of combustion engine |
| CN111734689A (en) * | 2020-07-02 | 2020-10-02 | 中国航发常州兰翔机械有限责任公司 | Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device |
| CN111734689B (en) * | 2020-07-02 | 2021-09-17 | 中国航发常州兰翔机械有限责任公司 | Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device |
Also Published As
| Publication number | Publication date |
|---|---|
| SG10201700926TA (en) | 2017-09-28 |
| CA2957487A1 (en) | 2017-08-19 |
| US20170239692A1 (en) | 2017-08-24 |
| EP3208430A1 (en) | 2017-08-23 |
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